Compressor turbine wheel
AssigneeRolls-Royce North American Technologies Inc.
InventorsDouglas David Dierksmeier, Michael A. Karam
Life of this patent
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Abstract
A turbine wheel for a gas turbine engine including a compressor impeller and a radial inflow turbine integral to or attached to the compressor impeller is provided. A compressor turbine wheel including features to increase surface area of a surface of the compressor impeller and/or the radial inflow turbine and/or a passage to flow air between the compressor impeller and the radial inflow turbine is further provided. Methods for cooling radial inflow turbines integral to compressor impellers are further provided.
Claims20
A compressor turbine wheel for a gas turbine engine, the compressor turbine wheel rotatable about a forward-aft axis passing through a forward-aft axial wheel bore at a center of the compressor turbine wheel, the compressor turbine wheel comprising:
- a compressor impeller comprising a forward impeller vane inlet, a radial impeller vane outlet configured to flow compressed air radially outward to a diffuser, an aft inner surface extending from the forward impeller vane inlet to the radial impeller vane outlet, and inner vane side walls projecting forward from the aft inner surface;
- and
- a radial inflow turbine aft of the compressor impeller and comprising a radial turbine vane inlet configured to receive combustion gases from a combustor, an aft turbine vane outlet, a forward inner turbine surface extending from the radial turbine vane inlet to the aft turbine vane outlet, and inner turbine vane side walls projecting aft from the forward inner turbine surface;
- and
- wherein the radial inflow turbine is integral to the compressor impeller.
A compressor turbine wheel for a gas turbine engine, the compressor turbine wheel rotatable about a forward-aft axis passing through a forward-aft axial wheel bore at a center of the compressor turbine wheel, the compressor turbine wheel comprising:
- a compressor impeller comprising a forward impeller vane inlet, a radial impeller vane outlet configured to flow compressed air radially outward to a diffuser, an aft inner surface extending from the forward impeller vane inlet to the radial impeller vane outlet, and inner vane side walls projecting forward from the aft inner surface;
- and
- a radial inflow turbine aft of the compressor impeller and comprising a radial turbine vane inlet configured to receive combustion gases from a combustor, an aft turbine vane outlet, a forward inner turbine surface extending from the radial turbine vane inlet to the aft turbine vane outlet, and inner turbine vane side walls projecting aft from the forward inner turbine surface;
- wherein the radial inflow turbine is integral to the compressor impeller, or an aft outer surface of the compressor impeller is fixed to a forward outer surface of the radial inflow turbine;
- and
- wherein a passage extends between the aft inner surface and the forward inner turbine surface.
A method of cooling a radial inflow turbine of a gas turbine engine rotatable about a forward-aft axis, comprising:
- transferring heat from the radial inflow turbine to a compressor impeller via conduction through the radial inflow turbine and the compressor impeller;
- and
- wherein the radial inflow turbine is integral to the compressor impeller, or an aft outer surface of the compressor impeller is fixed to a forward outer surface of the radial inflow turbine.
Dependencies are inferred from the claim text.